Blind landing system



Oct. 27, 1953 E. RlcHoN BLIND LANDING SYSTEM 5 Sheets-Sheet 1 Filed sept. 12, 1951 oct. 27, 1953 E, mcHON 2,657,381

BLIND vLANDING SYSTEM Filed Sept. 12, 1951 3 Sheets-Sheet 2 Inventor EMILE Rich/olv 0ct. 27, 1953 E. RlcHoN BLIND LANDING SYSTEM s ahnte-sheet s Filed Sept. 12, 1951 Inventor M, MNM my@ v 7 M Patented Oct. 27, '1953 UNI-.TED STATES PATENT FFIC signor to International Standard Electric Corporation, New York, N. Y., a corporation of Application-September 12, 1951,- Serial No.246g202 In France September 13, 1950- n 1 Claim. i`

The present invention relates to a blind landing system and more particularly to a system of this type utilising the radiation from a set of aerials in crder to define a landing trajectory for example by the process of equisignals utilising the comparison of two-highv frequency electro-magnetic fields modulated by suitable different frequencies for example 150 and 90 cycles per second.

In systems of this-type atv present known difficulties are met particularly for obtaining a correct line of landing without false trajectories. Further, the possible adjusting margins are very reduced for obtaining a suitable ratio of the two radiated fields. Finally, the neatness of the trajectories achieved` by known devices can Vary only within narrow limits.v

The present invention has for object to avoid these drawbacks and. to provide a number of advantages which will appear from a. reading of the. following description whilst making use of equipment at present. used for the ground installations without modifying.. the equipment on board of the aircrafts.

According to one of its features, the invention provides a system of aerials for defining the landing trajectory comprising three antennae located one above the other and located above the ground at heights substantially equal to h, 4h and 8h respectively.

Other objects, features and advantages of the present invention will appear from a reading of the following description of an embodiment of the present invention, the said description being given-inconnection with the accompanying drawings-inwhich:

Fig. 1 represents a known arrangement of antennae for guiding the landing of a craft in a blind landing system.

Fig. 2 represents a new arrangement embodying features of the invention for the antennae of a guiding system for the landing curve.

Figs. 3a, 3b and 3c represent various arrangements of the means for feeding the antennae represented in Fig. 2.

Figs. 4 and 5 represent respectively the amplitude of the radiated fields in function of the angle of the landing trajectory with respect to ground first in the case of the system of Fig. 1 land then in the case of that of Fig. 2.

Fig. 1 represents a known antenna device ladapted for defining a landing trajectory associated to a transmitter l supplying high frequency modulated energy on the one hand at .1.50 cycles and on the other hand at 90 cycles.

Z' The energy modulated at 150 cycles feeds the upper antenna 2 placed in front of a rect'r' 3 by means of a transmission line or feeder'4'. B- low the antenna 2 is placed an antenna 5 placed infront of a reflector 3f, and fed bymodulated energy at 9U cyclesby means of the trns- Initter l. Antenna 5 is placed? at a height` q'iial to h above the ground whereas antenna 2 is at a height substantially equal' to 4.75 aboveY the ground. Such an arrangement supported on a vertical post lll is well-knQwn in the art'. v

The device shown in Figure 2` embodies features of the invention and comprises as tlat if Fig. 1 a transmitter feeding with .modulated en"- ergy at 15'0 cycles and" with suitable phases' two antennae 6 andV 'l placed in front' of' a reflector El. These antennae and]f are fed'witlsitable phases by means ofy an impedance match"- ing system 9l which willbe described ltler'n' in details. Finally the antenna lll; placed alstA front of a reilectory 8",. is fed withV liiglfiV frquency energy modulated at cycles; the assembly is carried by a verticalpost l5. A f'eature of the device resides in this thatv the aii'- tenna` lil being atV a height h above the vii'tiial plane representing the ground; the antenna Tis at a height 4h and'nally the antenna 'S'is'at a height 8h.

Fig. 3a represents an experimental coupling device for the antennaeA 61.1 and IOwitla transmitter I producing modulated waves at cycles and atl 9D"v cycles. As seen-'en 3'z`z.,.th'e waves modulated at 150 cycles are applied' in parallel on antennae and lrepresentedonFig. 2. ToV obtain a suitable adjustment;- anadjuStable short-circuity correctingline: is provided in ll at a suitable distance from the derivation `point of the feeding line. Antenna lil, fed in energy modulated at 90 cycles is connected to a transmission line delivering from transmitter l and is equipped with a correcting line I2 in order to obtain the `desired adjustment in amplitude and in phase in antennae S, l and I0.

The device represented on Fig. 3b comprises a transmitter l producing energy modulated at 15'0 cycles and at 90 cycles as in the case of Fig. 3a. The arrangement of the output circuits of transmitter l comprises a circuit delivering energy modulated at 90 cycles and striking directly antenna I 0 at currents modulated at 90 cycles. The dividing of the energy modulated at 150 cycles is carried out in the same way as on Fig. 3a, but the derivation and the correcting line are located in the upper part of the feeding system of antennae 6 and l, for example on A.

3 The adjustment of these devices is carried out once for all, so that the phases in the antennae 'are xed permanently.

Another device could be the one represented on Fig. 3c which comprises an impedance transformer I3. This device can be located in the upper part of the antennae, on A for instance in Fig. 2.

Figs. 4 and 5 represent in Cartesian coordinates, on the one hand the diagram of radiation obtained by means of a known device represented in Fig. 1 whilst Fig. 5 represents the diagram of radiation obtained ,Withthe arrangement represented on Fig. 2. Y

On Fig. 4, it will be seen that the high frequency eld modulated at 150 cycles produces a series of loops I, 2, 3, 4, 5, 6, 1 etc., representing the amplitude of this field in relation to the angle a. between the line of propagation of the eld with the horizontal plan. On the other hand, the curves a, b, and vc of the field modulatedY at 90 cycles havebeen drawn for values of K=2, 1,5, 2, 1,08, K ,beingthe ratio between the amplitude of the modulated eld at 90 cycles at a given instant and the amplitude of the eld modulated at 150 cycles at theV same instant. Finally the curve K =2 (1i) of the field modulated Vat 90 cycles and K :2 andrfor a thickness of snow on the ground equalto 60 centimeters has also been drawn Ymodifying the position of the lvirtual plane representing the ground. n Y

Fig. 5 Y represents the high frequency ilelds modulated respectively at 150 and 90 cycles in the same conditions as on Fig. 4, but utilising the arrangement of the antennae and feedings represented on Fig.2. n f A v Y n The curves d, e, f representing the variation of the amplitude of the `eld modulated at 90 cycles in relation to the angle between the direction of propagation of the eld with the horizontal plane do not present anyY peculiarity, they are similar to those represented on Fig. 4. On the contrary the series of loops representing the variation of the amplitude of the modulated iield at 150 cycles in relation to the angle between the direction of propagation of the field and the horizontal plane undergoes variations of considerable amplitude. n

VThus thesecond and third, the sixth and seventh, the tenth and eleventh loops etc., are reduced to a very low amplitude and loops 4, 5, 8, 9 etc., reach the amplitude of loop l. The decrease in amplitude of loops 2 and 3 make it possible to locate the curve of the eld modulated at 90 cycles within very wide limits and can vary from K=1.25 to K=2.65. A very great latitude for the adjustment of the device is thus obtained. It is however desirable, in order to main- ALG 4 tain neatness in the signals which correspond to the regulations of international air navigation, to choose K, so that the curve of the eld modulated at cycles locates itself toward the middle of the interval comprised between the curves corresponding to K:1.25 and K=2.65. A wide range of possibilities for adjustment leading to the best possible results is thus obained.

Another advantage of the device according to the present invention consists in the possibility -of limiting the detrimental effects that produces with present day devices the presence of a thick layerV of snow on the ground Where the system of antennae is erected. In fact, the comparative study of the curves on Figs. 4 and 5 shows that in the case of Fig. 4 a layer of snow 60 centimeters thick causes at the passage of the loop 2 of the field modulated at cycles a considerable decrease of the difference in level, which is capable of causing on the indicator board a pseudo zero and inv consequence accidents on landing. On the contrary, with a layer of snow of an equal'thickness the device of Fig. 2 enables to obtain a diierence in level much greater in the neighbourhood of the highest loops of the eld modulated at 150 periods.

While the principles of the invention have been described above 4in connection with specic embodiments and particular modifications thereof, it is to be clearly understood that this description is made only by way of example and not as a limitation on the scope of theinvention.

What is claimed is:

In a landing system using an array of aerials for radiating two fields of electro-magnetic waves modulated with diierent characteristic signals, which waves are reflected from ground and in which the landing trajectory is determined by the equality of the different signals comprising the modulation of said waves, an aerial system comprising, a rst antenna mounted at a height h above the eiective ground plane, means for Ysupplying energy modulated with one of said characteristic signals to said first antenna, second and third antennae disposed above said lrst antenna at heights of 4h and 8h respectively, and means for supplying energy modulated with the other characteristic signal to said second and third antennae.

EMILE RICHON.

References Cited in the le of this patent v UNITED STATES PATENTS Number Name Date 2,379,442 Kandoian July 3, 1945 2,406,876 Watts Sept. 3, 1946 

